Dynamic stall control over an airfoil by NS-DBD actuation*

Yang, Hesen; Zhao, Guiping; Liang, Hua; Wei, Biao

doi:10.1088/1674-1056/abb227

Cited by 7 publications

(7 citation statements)

References 34 publications

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“…As we know, for a static airfoil's separation control, the actuation's control effect extensively depends on the airfoil's α, and the stall can only be delayed by 2-3 degrees [9]. This means that the plasma actuation has a range of capabilities, and it has no effect at the small angle of attack where the leading edge does not separate and the high α is much larger than the stall α.…”

Section: Discussion On Control Effects Of Different F + In Unsteady A...mentioning

confidence: 99%

“…During the past 10 years, the dielectric barrier discharge (DBD) plasma actuation has been extensively researched due to its advantages of simple construction, no moving components, broad frequency band and fast response. Recently, nanosecond dielectric barrier discharge (NS-DBD) has attracted attention in the field of dynamic stall control by virtue of its stronger disturbance ability to the flow field [8,9], while alternating current dielectric barrier discharge (AC-DBD) is the most widely used actuation method. Compared with NS-DBD, AC-DBD has smaller electromagnetic interference.…”

Section: Introductionmentioning

confidence: 99%

“…The discharge parameter testing system consists of a highvoltage probe, current probe and digital oscilloscope to measure the discharge voltage and current of the actuator [9]. Figure 3 shows the voltage(V )-current(I) signals collected when the actuation peak-to-peak voltage V p-p =9 kV, the pulsed actuation frequency f p =200 Hz, and the duty ratio DC=50%.…”

Section: Experimental System Design and Introductionmentioning

confidence: 99%

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Experimental study on dynamic stall control based on AC-DBD actuation

Yang

Liang

Zhao

et al. 2021

Plasma Sci. Technol.

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To explore AC-DBD's ability in controlling dynamic stall, a practical SC-1095 airfoil of a helicopter was selected, and systematic wind tunnel experiments were carried out through direct aerodynamic measurements. The effectiveness of dynamic stall control under steady and unsteady actuation is verified. The influence of parameters such as constant actuation voltage, pulsed actuation voltage, pulsed actuation frequency and duty ratio on dynamic stall control effect is studied under the flow condition of k=0.15 above the airfoil, and the corresponding control mechanism is discussed. Steady actuation can effectively reduce the hysteresis loop area of dynamic lift, and control the peak drag and moment coefficient. For unsteady actuation, there is an optimal duty ratio DC=50%, which has the best effect in improving the lift and drag characteristics, and there is a threshold of pulsed actuation voltage in dynamic stall control. The optimal dimensionless frequency will not be found; different F + have different control advantages in different aerodynamic coefficients of different pitching stages. Unsteady actuation has obvious control advantages in improving the lift-drag characteristics and hysteresis, while steady actuation can better control the large nose-down moment.

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Section: Discussion On Control Effects Of Different F + In Unsteady A...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Experimental System Design and Introductionmentioning

confidence: 99%

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Experimental study on dynamic stall control based on AC-DBD actuation

Yang

Liang

Zhao

et al. 2021

Plasma Sci. Technol.

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“…In the work of Singhal et al [31], the aerodynamic hysteresis effect and DSV strength were reduced by nanosecond DBD plasma (NS-DBD) actuators, and the DSV was completely eliminated by sufficiently high actuation frequency. Yang et al [32] also used NS-DBD to explore the flow control effects on airfoil dynamic stall at a Reynolds number of 5.8×10 5 ; DBD actuation performed more effectively in the downstroke stage, and the control effect gradually became weaker with a reduced frequency increase. Li and Yi [33] applied a large eddy simulation numerical calculation to verify the plasma unsteady actuation mechanism on dynamic stall, the results showed that the separation vortices are broken and dissipated by the DBD actuation, and led to a strong nonlinear oscillation of aerodynamic force caused by the interaction between dynamic vortex structures with plasma actuation.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of dynamic stall flow control using a microsecond-pulsed plasma actuator

Zeyang

Gao

et al. 2023

Plasma Sci. Technol.

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To alleviate the performance deterioration caused by dynamic stall of the wind turbine airfoil, the flow control by microsecond-pulsed dielectric barrier discharge (MP-DBD) actuator on the dynamic stall of a periodically pitching NACA0012 airfoil was investigated experimentally. The unsteady pressure measurements with high temporal accuracy were employed in this study, and the unsteady characteristics of the boundary layer were investigated by wavelet packet analysis and the moving root mean square (RMS) method based on the acquired pressure. The experimental Mach number was Ma =0.2, and the chord-based Reynolds number was Re = 870000. The dimensionless actuation frequencies F+ were chosen to be 0.5, 1, 2, and 3, respectively. For the light dynamic regime, the MP-DBD plasma actuator plays the role of suppressing flow separation from the trial edge and accelerating the flow reattachment due to the high momentum freestream flow being entrained into the boundary layer. Meanwhile, actuation effects were promoted with the increasing dimensionless actuation frequency F+. The control effects of the deep dynamic stall were to delay the onset and reduce the strength of the dynamic stall vortex (DSV), due to the accumulating vorticity near the leading edge being removed by the induced coherent vortex structures. The laminar fluctuation and K-H (Kelvin-Helmholtz) instabilities of transition and relaminarization were also mitigated by the MP-DBD actuation, and the alleviated K-H rolls lead to the delay of the transition onset and earlier laminar reattachment, which improved the hysteresis effect of the dynamic stall. For the controlled cases of F+ = 2, and F+ = 3, the laminar fluctuation was replaced by relatively low frequency band disturbances corresponding to the harmonic responses of the MP-DBD actuation frequency.

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“…It has attracted wide attention in recent years and is widely used in biomedicine [12][13][14][15][16], environmental purification [17][18][19][20], catalytic technology [21][22][23][24], material handling [25][26][27], flow control, and other fields. Surface Dielectric Barrier Discharge (SDBD) [28] which has the advantages of easy adhesion, rapid response, and adjustable parameters, has been widely used in the fields of stall control [29][30][31][32][33][34], boundary layer rotation [35][36][37][38][39][40], lift enhancement [41][42][43], anti-icing [44][45][46][47][48] and other flow separation control applications. Surface dielectric barrier discharge is classified as Alternating Current Dielectric Barrier Discharge (AC-DBD), Microsecond Dielectric Barrier Discharge (µS-DBD), and Nanosecond Dielectric Barrier Discharge (NS-DBD), of which AC-DBD and NS-DBD are more widely used than µS-DBD.…”

Section: Introductionmentioning

confidence: 99%

Flow Separation Control of Nacelle Inlets in Crosswinds by Dielectric Barrier Discharge Plasma Actuation

et al. 2023

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Crosswinds will lead to large-scale flow separation in the nacelle inlets, which seriously affects the flight safety of the aircraft; there is an urgent need to develop flow control measures. As a plasma flow control method, the application of surface dielectric barrier discharge in the field of nacelle inlet separation control is of great significance for improving the intake quality. Based on the characteristic law of the baseline flow field, the flow control effect of the nacelle inlet separation flow field experiments with NS-DBD, and the influence of the actuation frequency on the flow control is discussed. A comparative experimental study of NS-DBD and AC-DBD is carried out. Finally, the flow control mechanisms for both are discussed. The results show that under the condition that the flow velocity of the wind tunnel is 35 m/s and the crosswind angle is 10°, the average total pressure loss coefficient and distortion index decrease by 29.62% and 44.14% by NS-DBD actuation. At the same time, exists an inherent optimal coupling frequency in NS-DBD, and the control effect of NS-DBD is better than that of AC-DBD. NS-DBD mainly through shock waves and induced vortices, while AC-DBD mainly through the induced generation of near-wall jets to reduce the inverse pressure gradient and improve nacelle flow separation.

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Dynamic stall control over an airfoil by NS-DBD actuation*

Cited by 7 publications

References 34 publications

Experimental study on dynamic stall control based on AC-DBD actuation

Experimental study on dynamic stall control based on AC-DBD actuation

Experimental investigation of dynamic stall flow control using a microsecond-pulsed plasma actuator

Flow Separation Control of Nacelle Inlets in Crosswinds by Dielectric Barrier Discharge Plasma Actuation

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